叶片前缘前掠与分流叶片偏置对高海拔压气机流动特性的影响
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摘要
为提高离心压气机和涡轮增压器的工作性能,基于CFD仿真软件,开展高海拔下叶片前缘前掠与分流叶片偏置对压气机流动特性影响规律的研究。结果表明:在叶片前缘前掠角为6. 27°、分流叶片与主叶片吸力面夹角为12. 09°的情况下,叶轮不同叶高截面内低能流体范围减小,分流叶片吸力面一侧通道内损失明显降低;分流叶片吸力面一侧相互卷吸的低能流体占据流道宽度约为优化前叶轮的一半,对主叶片流体流动的干扰有所减弱;出口处各叶高损失均小于优化前,从80%叶高开始存在明显的降低,且靠近分流叶片吸力面一侧损失减小更为显著。
To improve the performance of a centrifugal compressor and turbocharger,the paper applies CFD simulation software to study high-attitude flow characteristics of a compressor with blade leading edges swept forward and splitter blades biased,contributing to three conclusions. Firstly,when the forward-sweeping angle is 6. 28 degrees and the angle between the splitter blade and suction surface of main blade angle is 12. 09 degrees,an impeller would have a decrease in the range of low-energy fluid in sections along different leaf heights,and an obvious reduction in loss of the channel near the suction surface. Secondly,low-energy fluid entraining on the side of suction surface occupies about half of the runner width of nonoptimized impeller,and acts less on the flow of main stream. Finally,the loss at the outlet along each leaf height is lower than that before optimization,with a remarkable decrease from 80 percent of leaf height and a more notable reduction near the suction surface.
To improve the performance of a centrifugal compressor and turbocharger,the paper applies CFD simulation software to study high-attitude flow characteristics of a compressor with blade leading edges swept forward and splitter blades biased,contributing to three conclusions. Firstly,when the forward-sweeping angle is 6. 28 degrees and the angle between the splitter blade and suction surface of main blade angle is 12. 09 degrees,an impeller would have a decrease in the range of low-energy fluid in sections along different leaf heights,and an obvious reduction in loss of the channel near the suction surface. Secondly,low-energy fluid entraining on the side of suction surface occupies about half of the runner width of nonoptimized impeller,and acts less on the flow of main stream. Finally,the loss at the outlet along each leaf height is lower than that before optimization,with a remarkable decrease from 80 percent of leaf height and a more notable reduction near the suction surface.
引文
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[2] GO T H,MAQSOOD A. Effect of aspect ratio on wing rock atlow Reynolds number[J]. Aerospace Science&Technology,2015,42:267-273.
[3]霍磊,刘火星.低雷诺数下离心压气机性能及流动影响的数值研究[J].航空动力学报,2013,28(4):911-920.
[4]陈浮,王云飞,陈焕龙,等.雷诺数对带蜗壳的离心压气机内部流场影响研究[J].推进技术,2013,34(7):911-917.
[5]王云飞.雷诺数对离心压气机性能影响的研究[D].哈尔滨:哈尔滨工业大学,2012.
[6]刘卓学,董素荣,张众杰,等.高原环境对离心压气机气动性能及流动特性的影响[J].军事交通学院学报,2017,19(8):47-52.